Electrical machines

• US 10,221,730 B2
• Filed: 11/30/2015
• Issued: 03/05/2019
• Est. Priority Date: 12/18/2014
• Status: Active Grant

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Adams, Edward, Chong, Ellis Ful Hen, Moliner-Cantos, Fermin
• Primary Examiner(s): Patel, Tulsidas C
• Assistant Examiner(s): Ortega, Joseph
• Application Number:
  US14/954,320
• Publication Number:
  US 20160177770A1
• Time in Patent Office: 1,191 Days
• Field of Search: 290 46, 290 52, 290 40 R, 290 4 R
• CPC Class Codes: F01D 15/10 Adaptations for driving, or combinations with, electric generators
• CPC Class Codes: F01L 15/10 with main slide valve and auxiliary valve dragged thereby
• CPC Class Codes: F02C 7/26 Starting; Ignition
• CPC Class Codes: H02K 1/14 Stator cores with salient poles
• CPC Class Codes: H02K 1/17 Stator cores with permanent magnets
• CPC Class Codes: H02K 16/04 Machines with one rotor and two stators
• CPC Class Codes: H02K 19/103 Motors having windings on the stator and a variable reluctance soft-iron rotor without windings
• CPC Class Codes: H02K 7/116 with gears
• CPC Class Codes: H02K 7/1823 structurally associated with turbines or similar engines

Abstract

An arrangement of electrical machines including: a variable reluctance rotor. The arrangement also including an annular array of stators; each stator configured to function, in conjunction with the rotor, as an electrical machine.

Claims

1. A gas turbine engine comprising:

a rotor stage;

a variable reluctance rotor without windings or magnets; and

an annular array of stators, each stator configured to function, in conjunction with the variable reluctance rotor, as an electrical machine,

wherein the stators are irregularly spaced,

wherein each irregularly spaced stator extends along a circumference of the variable reluctance rotor by a different amount than at least one stator adjacent to the each stator, and

wherein the variable reluctance rotor is integral with or mounted to the radial periphery of the rotor stage.

2. The gas turbine engine as claimed in claim 1, wherein each stator is self-exciting.

3. The gas turbine engine as claimed in claim 1, wherein the rotor comprises a magnetically permeable material.

4. The gas turbine engine as claimed in claim 1, further comprising a circumferential gap between adjacent stators.

5. The gas turbine engine as claimed in claim 1, wherein each stator has a circumferential extent of up to 180°

.

6. The gas turbine engine as claimed in claim 1, wherein each stator comprises any or all of:

one or more windings; and

one or more permanent magnets or electromagnets.

7. The gas turbine engine as claimed in claim 1, wherein the rotor is radially outside the array of stators.

8. The gas turbine engine as claimed in claim 1, wherein the rotor is formed of two or more pieces, the pieces being joined during use of the arrangement and being detached for assembly and/or disassembly of the arrangement.

9. The gas turbine engine as claimed in claim 1, wherein at least one of the stators is configured as a 3-phase generator or as a motor.

10. The gas turbine engine as claimed in claim 1, comprising at least three stators, each stator configured as a phase of a distributed multi-phase generator.

11. The gas turbine engine as claimed in claim 1, wherein at least one of the stators is configured to output the speed and/or acceleration of the rotor.

12. The gas turbine engine as claimed in claim 1, wherein the output of at least two of the stators is coupled, and wherein one of the stators comprises a rectifier.

13. The gas turbine engine as claimed in claim 1, wherein the rotor is coupled to a shaft of a gearbox, wherein the shaft is an input shaft or an output shaft.

14. The gas turbine engine as claimed in claim 13, wherein the gearbox is an epicyclic gearbox.

15. The gas turbine engine as claimed in claim 1, wherein the output of each electrical machine is coupled to a load, the loads comprising any one or more of:

a breather arrangement in a gas turbine engine;

one or more tunnel or steering thrusters for a marine vessel;

a pump for a submarine;

a cooling pump for a nuclear power plant;

an oil pump;

a fuel pump;

an engine controller for a gas turbine engine;

a starter for a gas turbine engine;

aircraft electrical loads;

actuators for moving variable geometry in a gas turbine engine;

anti-icing heating arrangements in a gas turbine engine;

rotation of a shaft after shut-down.

16. The gas turbine engine as claimed in claim 1, wherein the rotor stage comprise any one of:

a fan;

a stage of an intermediate pressure compressor;

a stage of a high pressure compressor;

a stage of a booster compressor;

a stage of a high pressure turbine;

a stage of an intermediate pressure turbine; and

a stage of a low pressure turbine.

17. A gas turbine engine comprising:

at least two axially spaced rotor stages;

a variable reluctance rotor without windings or magnets; and

an annular array of stators, each stator configured to function, in conjunction with the variable reluctance rotor, as an electrical machine,

wherein the stators are irregularly spaced,

wherein each irregularly spaced stator extends along a circumference of the variable reluctance rotor by a different amount than at least one stator adjacent to the each stator, and

wherein the variable reluctance rotor is integral with or mounted to the radial periphery of two of the rotor stages.

18. The gas turbine engine as claimed in claim 17, wherein the rotor stages comprise any one of:

a fan;

a stage of an intermediate pressure compressor;

a stage of a high pressure compressor;

a stage of a booster compressor;

a stage of a high pressure turbine;

a stage of an intermediate pressure turbine; and

a stage of a low pressure turbine.